The problem of stress analysis of swept wings has been approached in different ways. Here a method is briefly surveyed in which swept structures are treated as orthotropic sandwich plates of varying thickness; the resulting non‐linear partial differential equation is linearized by suitable assumptions. Thus differential bending, flexure‐torsion coupling, etc. can be treated with ease, and no virtual elastic axis is needed. Functions derived are regarded as two‐dimensional analogues of the well‐known concepts of one‐dimensional Engineers beam theory.
Terner, E. (1954), "Some Remarks on the Structural Analysis of Swept Wings: A Brief Account of a Method in which Swept Wings are Treated as Orthotropic Sandwich Plates", Aircraft Engineering and Aerospace Technology, Vol. 26 No. 9, pp. 288-291. https://doi.org/10.1108/eb032467
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